Unmanned aerial vehicle detection equipment

Abstract

The invention relates to the technical field of unmanned aerial vehicle detection, and discloses unmanned aerial vehicle detection equipment, and the equipment comprises a mounting seat which comprises a supporting frame which is fixedly disposed on a carrier; the transfer frame is arranged above the supporting frame, an opening is formed in the transfer frame, and a first air duct is formed between the transfer frame and the supporting frame; the vibration reduction parts are connected between the supporting frame and the transfer frame, and the multiple vibration reduction parts are arranged on the two sides in the first direction correspondingly; the equipment body comprises a shell and a circuit module, the two sides of the shell in the first direction are fixedly connected to the adapter frame, the top and the bottom of the shell are each provided with a plurality of heat dissipation fins extending in the second direction, at least part of the heat dissipation fins located at the bottom of the shell extend into the first air channel from the opening, and the circuit module is attached and fixed to the inner wall of the shell. By means of the mode, the unmanned aerial vehicle can be accurately detected and positioned in the scene of moving along with the carrier, and efficient heat dissipation of equipment can be achieved at low cost.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle detection, and particularly relates to an unmanned aerial vehicle detection device. BACKGROUND

[0002] With the rapid development and popularization of unmanned aerial vehicle technology, more and more fields are facing the challenge of low-altitude security threats, and unmanned aerial vehicle detection and countermeasures are one of the important means to cope with low-altitude security threats.

[0003] At present, most unmanned aerial vehicle detection devices are fixed or handheld, which cannot meet the needs of fast-moving scenes. Moreover, for these types of unmanned aerial vehicle detection devices, since the internal circuit elements generate a large amount of heat, a fan needs to be configured for active heat dissipation, which undoubtedly increases the cost of the product. SUMMARY

[0004] In view of the above problems, the embodiments of the present application provide an unmanned aerial vehicle detection device, which can not only accurately realize the detection and positioning of unmanned aerial vehicles in the scene of moving with a carrier, but also realize efficient heat dissipation of the device at a lower cost.

[0005] According to an aspect of the embodiments of the present application, an unmanned aerial vehicle detection device is provided, comprising: a mounting seat, comprising: a support frame for fixedly mounting on a carrier; an adapter frame arranged above the support frame, the adapter frame being provided with an opening, and a first air duct being formed between the bottom of the adapter frame and the top of the support frame; a damping member connected between the top of the support frame and the bottom of the adapter frame, the damping member comprising a plurality of members and being arranged on both sides of the support frame and the adapter frame along a first direction, wherein the first direction is perpendicular to the moving direction of the carrier; a device body, comprising: a shell fixedly connected to the adapter frame on both sides along the first direction, the top and the bottom of the shell being provided with a plurality of heat dissipation fins extending along a second direction, the plurality of heat dissipation fins being arranged at intervals along the first direction, and the heat dissipation fins located at the bottom of the shell at least partially extending into the first air duct from the opening, wherein the second direction is perpendicular to the first direction; and a circuit module fixedly attached to the inner wall of the shell.

[0006] In an optional manner, the shell is provided with a support arm on both sides along the first direction, and the support arm is lapped and fixed to the adapter frame.

[0007] In an optional manner, the device body further comprises a shielding cover and an antenna, the shielding cover covers the heat dissipation fins on the top of the shell, the antenna is arranged on the shielding cover, and the antenna is electrically connected with the circuit module; the shielding cover is provided with a ventilation opening on both sides along the second direction, and the ventilation opening is arranged opposite to the heat dissipation fins on the top of the shell.

[0008] In one alternative embodiment, the drone detection device also includes a protective cover covering the top and sides of the device body, shield, and antenna; an adapter is provided with ventilation openings on both sides of the housing along the second direction, the bottom edge of the protective cover is connected to the adapter, and a second air duct is formed between the housing and the protective cover on both sides along the second direction.

[0009] In one alternative embodiment, the vent includes an air inlet and an air outlet, with the air inlet located on the front side of the housing along a second direction and the air outlet located on the rear side of the housing along the second direction, and the area of ​​the air inlet being larger than the area of ​​the air outlet.

[0010] In one alternative embodiment, the housing and the opening are spaced apart at the front edge along the second direction to form an air inlet; the housing is provided with an interface along the front side of the second direction for connecting to an external device via a wiring harness, and the air inlet is for the wiring harness to pass through.

[0011] In one alternative embodiment, the damping component includes a first connecting block, a second connecting block, and damping springs; the first connecting block is fixed to the top of the support frame, the second connecting block is fixed to the bottom of the adapter frame, and the first and second connecting blocks are arranged opposite each other in a vertical direction, wherein the vertical direction is perpendicular to both the first and second directions; the damping springs extend helically and are respectively inserted into and fixed to the first and second connecting blocks; the axial direction of each damping spring is parallel to the second direction.

[0012] In one alternative configuration, the damping spring is divided into a first part and a second part along the axial direction, the first part and the second part being mirror-symmetrical with respect to a plane perpendicular to the second direction.

[0013] In one alternative approach, multiple vibration damping elements are provided between the support frame and the adapter frame on each side along the first direction.

[0014] In one alternative embodiment, the housing comprises an upper housing and a lower housing, the upper housing and the lower housing being interlocked and rotatably connected on one side.

[0015] The drone detection device provided in this application embodiment increases the contact area with the outside air by setting heat dissipation fins on the top and bottom of the shell, enabling the heat generated by the internal circuit modules to be quickly conducted to the outside environment. The heat dissipation fins extend along a second direction (i.e., the direction of movement of the carrier), so that even without a fan, airflow can quickly pass through the gaps between the heat dissipation fins as the shell moves with the carrier, thereby efficiently removing heat from the heat dissipation fins and improving heat dissipation efficiency.

[0016] For the mounting base that serves to install and dampen vibration, an opening is set on its adapter frame, and the heat dissipation fins at the bottom of the housing extend through the opening into the first air duct between the adapter frame and the support frame. This allows the airflow to flow quickly through the heat dissipation fins in the first air duct under the guidance of the adapter frame and the support frame, ensuring heat dissipation while making full use of the height space to reduce the overall height of the UAV detection equipment, giving it a lower center of gravity and greater stability.

[0017] In order not to affect the flow of gas in the first air duct, the vibration damping components between the support frame and the adapter frame are arranged on both sides along the first direction (perpendicular to the second direction). At the same time, the housing is connected to the adapter frame on both sides along the first direction, thereby perfectly avoiding the space at both ends of the first air duct along the second direction, so that the airflow can flow more fully and stably through the heat dissipation fins in the first air duct, ensuring the heat dissipation rate.

[0018] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0019] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 and Figure 2 These are two perspective views of the drone detection equipment provided in the embodiments of this application; Figure 3 and Figure 4 These are exploded views from two perspectives of the drone detection equipment provided in the embodiments of this application; Figure 5 An assembly drawing of the mounting base and housing in the UAV detection device provided in the embodiments of this application; Figure 6 An assembly drawing of the housing, shielding cover, and antenna in the UAV detection device provided in the embodiments of this application; Figure 7 and Figure 8 These are assembly drawings from two perspectives of the shell, adapter frame, and protective cover in the UAV detection equipment provided in the embodiments of this application; Figure 9 An exploded view of the mounting base in the UAV detection equipment provided in this application embodiment; Figure 10A side view of the vibration damping component in the UAV detection device provided in the embodiments of this application; Figure 11 This is a top view of the housing of the drone detection device provided in the embodiment of this application in the open state.

[0020] The reference numerals in the detailed embodiments are as follows: 10. Unmanned aerial vehicle (UAV) detection equipment; 100. Mounting base; 110. Support frame; 120. Adapter frame; 121. Opening; 130. Vibration damper; 131. First connecting block; 132. Second connecting block; 133. Vibration damping spring; 1331. First part; 1332. Second part; 141. First air duct; 142. Second air duct; 150. Ventilation opening; 151. Air inlet; 152. Air outlet; 200. Equipment body; 210. Housing; 211. Heat dissipation fins; 212. Support arm; 213. Interface; 214. Upper housing; 215. Lower housing; 220. Circuit module; 221. Spectrum detection module; 222. Detection and control processing module; 223. Overall control and scheduling module; 224. Power conversion module; 225. Communication routing module; 226. Power divider module; 227. Communication antenna; 230. Shielding cover; 231. Ventilation opening; 240. Antenna; 300. Protective cover. Detailed Implementation

[0021] The embodiments of the technical solution of this application will now be described in detail with reference to the accompanying drawings. These embodiments are only used to more clearly illustrate the technical solution of this application and are therefore merely examples, and should not be used to limit the scope of protection of this application.

[0022] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.

[0023] In the description of the embodiments of this application, technical terms such as "first" and "second" are used only to distinguish different objects and should not be construed as indicating or implying relative importance or implicitly specifying the number, specific order, or primary and secondary relationship of the indicated technical features. In the description of the embodiments of this application, "multiple" means two or more, unless otherwise explicitly defined.

[0024] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0025] In the description of the embodiments in this application, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent three cases: A exists, A and B exist simultaneously, and B exists. In addition, the character " / " in this document generally indicates that the related objects before and after it have an "or" relationship.

[0026] In the description of the embodiments of this application, the term "multiple" refers to two or more (including two), similarly, "multiple sets" refers to two or more (including two sets), and "multiple pieces" refers to two or more (including two pieces).

[0027] In the description of the embodiments of this application, the technical terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the embodiments of this application and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the embodiments of this application.

[0028] In the description of the embodiments of this application, unless otherwise expressly specified and limited, technical terms such as "installation," "connection," "joining," and "fixing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in the embodiments of this application can be understood according to the specific circumstances.

[0029] For drone detection equipment used in mobile applications, such as vehicle-mounted, ship-mounted, and airborne scenarios, the vibrations generated by the rapid movement of the carrier not only affect the accuracy of drone detection and positioning but also easily damage the internal components of the detection equipment. Therefore, vibration reduction is essential for achieving accurate drone detection and positioning in mobile environments.

[0030] To address this, this application first equips the equipment body with a vibration-damping mounting base to reduce vibrations transmitted from the vehicle body to the equipment body during operation. Considering that the installation of the mounting base would increase the height of the detection equipment, this application has made corresponding structural designs for the mounting base to minimize the overall height of the detection equipment, ensuring that it has a low center of gravity and good stability.

[0031] Meanwhile, in a work scenario where the device moves rapidly along with the carrier, the device will move relative to the surrounding airflow. If this motion relationship is utilized, a cooling effect that is similar to or even better than that of a fan-equipped cooling method can be achieved in a fanless structure.

[0032] Based on the above concept, and according to one aspect of an embodiment of this application, a drone detection device is proposed, for details please refer to [link / reference]. Figures 1 to 4 ,in Figure 1 and Figure 2 The three-dimensional structure of the UAV detection equipment is shown from two different perspectives. Figure 3 and Figure 4 The explosion structure of the drone detection equipment is shown from two different perspectives.

[0033] like Figure 1 and Figure 2 As shown, the UAV detection device 10 includes a mounting base 100 and a device body 200. The device body 200 is the main body that integrates the circuit structure required to realize the UAV detection function, while the mounting base 100 is responsible for the installation, fixation and vibration reduction of the device body 200 on a carrier (such as a vehicle body, ship body or aircraft body).

[0034] like Figure 3 and Figure 4 As shown, the mounting base 100 includes a support frame 110, an adapter frame 120, and a vibration damper 130. The support frame 110 is used for fixed installation on the carrier, specifically by means of threaded fasteners, suction cups, magnetic attraction, etc. The adapter frame 120 is located above the support frame 110, and the vibration damper 130 is connected between the top of the support frame 110 and the bottom of the adapter frame 120. The vibration damper 130 can be a spring, leaf spring, hydraulic damping shock absorber, air suspension shock absorber, etc., and is not limited here.

[0035] The device body 200 includes a housing 210 and a circuit module 220. The circuit module 220 is attached and fixed to the inner wall of the housing 210, and the heat generated by the circuit module 220 during operation is transferred to the housing 210.

[0036] The top and bottom of the housing 210 are provided with a plurality of heat dissipation fins 211 extending along a second direction (indicated by the double arrow Y in the figure, which is the direction of movement of the carrier). The plurality of heat dissipation fins 211 are arranged at intervals along a first direction (indicated by the double arrow X in the figure, which is perpendicular to the direction of movement of the double arrow Y). By extending the heat dissipation fins 211 along the direction of movement of the carrier, the airflow outside the housing 210 can quickly flow through the gaps between adjacent heat dissipation fins 211 as the housing 210 moves with the carrier, so as to quickly remove the heat from the heat dissipation fins 211. Thus, efficient heat dissipation of the circuit module 220 inside the housing 210 is achieved without the need for a fan to drive and guide the airflow.

[0037] In order to complete the deployment of the vibration damping component 130 without affecting the rapid airflow at the heat dissipation fins 211, and to minimize the overall height of the UAV detection device 10, ensuring that it has a low center of gravity and good stability, this application improves the assembly form between the housing 210 and the mounting base 100.

[0038] For details, please continue reading Figure 3 and Figure 4 In, and further combined Figure 5 The assembly structure of the housing 210 and the mounting base 100 is shown. An opening 121 is provided on the adapter frame 120. A first air duct 141 is formed between the bottom of the adapter frame 120 and the top of the support frame 110. Space needs to be reserved between the top of the support frame 110 and the bottom of the adapter frame 120 to accommodate the vibration damping component 130; this reserved space serves as the first air duct 141. At least a portion of the heat dissipation fins 211 located at the bottom of the housing 210 extends from the opening 121 into the first air duct 141.

[0039] This configuration not only allows for the utilization of the space between the support frame 110 and the adapter frame 120, reducing the height of the UAV detection device 10, but also guides and restricts airflow when the carrier moves, allowing the airflow to flow stably from the space between the adapter frame 120 and the support frame 110 through the heat dissipation fins 211 at the bottom of the housing 210, thereby quickly removing the heat from the bottom heat dissipation fins 211.

[0040] It should be noted that, in order to ensure that there is a certain amount of room for movement between the housing 210 and the support frame 110 in order to meet the vibration reduction requirements of the housing 210, after the heat dissipation fins 211 at the bottom of the housing 210 extend into the first air duct 141, a certain gap needs to be reserved between it and the support frame 110 below it, so that the housing 210 can move relative to the support frame 110.

[0041] To prevent interference with the airflow in the first air duct 141 and to avoid affecting the heat dissipation effect of the heat sink 211 at the bottom of the casing 210, such as Figures 3 to 5 As shown, multiple vibration dampers 130 are provided and are respectively disposed on both sides of the support frame 110 and the adapter frame 120 in the direction indicated by the double arrow X, thereby allowing the vibration dampers 130 to avoid the first air duct 141 and ensuring that they do not interfere with the airflow of the first air duct 141.

[0042] Similarly, the housing 210 is fixedly connected to the adapter 120 on both sides in the direction indicated by the double arrow X, so as to ensure that the heat dissipation fins 211 at the bottom of the housing 210 are not obstructed on the front and rear sides in the direction indicated by the double arrow Y, and to ensure that the airflow passes through the heat dissipation fins 211 at the bottom efficiently and smoothly.

[0043] Regarding the specific assembly method of the housing 210 on the adapter frame 120, this application proposes an implementation scheme, as follows: Figure 3 and Figure 5 As shown, the housing 210 has support arms 212 on both sides along the direction indicated by the double arrow X. The support arms 212 are overlapped and fixed to the adapter frame 120. During assembly, the housing 210 can be initially positioned on the adapter frame 120 by the support arms 212 on both sides. At this time, the housing 210 can be stably held on the adapter frame 120 without the need for manual support, thus effectively reducing the difficulty of assembly. Then, the support arms 212 can be fixedly connected to the adapter frame 120 by means of screws, etc., and the assembly between the housing 210 and the adapter frame 120 can be easily completed.

[0044] In summary, the UAV detection device 10 provided in this application embodiment increases the contact area with the outside air by providing heat dissipation fins 211 on the top and bottom of the housing 210, enabling the heat generated by the internal circuit module 220 to be quickly conducted to the outside environment. The heat dissipation fins 211 extend along the second direction (i.e., the direction of movement of the carrier), so that even without a fan, airflow can quickly flow through the gaps between the heat dissipation fins 211 as the housing 210 moves with the carrier, thereby efficiently removing heat from the heat dissipation fins 211 and improving heat dissipation efficiency.

[0045] For the mounting base 100, which serves to install and dampen vibration, an opening 121 is provided on its adapter frame 120, and the heat dissipation fins 211 at the bottom of the housing 210 extend through the opening 121 into the first air duct 141 between the adapter frame 120 and the support frame 110. This allows the airflow to flow quickly through the heat dissipation fins 211 in the first air duct 141 under the guidance of the adapter frame 120 and the support frame 110, ensuring heat dissipation while making full use of the height space to reduce the overall height of the UAV detection device 10, giving it a lower center of gravity and stronger stability.

[0046] In order not to affect the flow of gas in the first air duct 141, the vibration damping component 130 between the support frame 110 and the adapter frame 120 is arranged on both sides along the first direction (perpendicular to the second direction). At the same time, the housing 210 is connected to the adapter frame 120 on both sides along the first direction. This perfectly avoids the space at both ends of the first air duct 141 along the second direction, so that the airflow can flow more fully and stably through the heat dissipation fins 211 in the first air duct 141, ensuring the heat dissipation rate.

[0047] Please refer to it again. Figure 3 and Figure 4 and further combine Figure 6 In some embodiments, the device body 200 may further include a shielding cover 230 and an antenna 240. The shielding cover 230 covers the heat dissipation fins 211 on the top of the housing 210, and the antenna 240 is disposed on the shielding cover 230. The antenna 240 is electrically connected to the circuit module 220. Specifically, the electrical connection between the antenna 240 and the circuit module 220 can be achieved by making holes in the shielding cover 230 and the housing 210 for wiring. The shielding cover 230 and the housing 210 work together to achieve electromagnetic shielding between the antenna 240 and the circuit module 220, thereby preventing the circuit module 220 from being affected by electromagnetic interference from the antenna 240.

[0048] Since the shielding cover 230 covers the top heat sink 211, in order to prevent affecting the heat dissipation of the top heat sink 211, such as Figure 6 As shown, ventilation openings 231 are provided on both sides of the shield 230 along the direction indicated by the double arrow Y. The ventilation openings 231 are arranged opposite to the heat dissipation fins 211 on the top of the housing 210. Airflow can enter and exit the shield 230 through the ventilation openings 231 on both sides to remove the heat from the heat dissipation fins 211 inside the shield 230.

[0049] Considering that the drone detection equipment 10 is mostly used in outdoor scenarios when installed on a carrier, in order to effectively cope with harsh outdoor environments, such as Figures 1 to 4 As shown, the UAV detection device 10 also includes a protective cover 300, which covers the top and sides of the device body 200, the shield 230 and the antenna 240 to provide protection and prevent damage to the antenna 240 and the circuit module 220 inside the housing 210 caused by rain, sandstorms and other weather conditions.

[0050] Please combine further Figure 7The assembly structure of the housing 210, adapter frame 120, and protective cover 300 shown is such that the adapter frame 120 has ventilation openings 150 on both sides of the housing 210 along the direction indicated by the double arrow Y. The bottom edge of the protective cover 300 is connected to the adapter frame, and a second air duct 142 is formed between the two sides of the housing 210 and the protective cover 300 along the direction indicated by the double arrow Y. With this arrangement, a portion of the air entering the first air duct 141 between the adapter frame 120 and the support frame 110 will enter the second air duct 142 from the ventilation opening 150 on one side, and further flow through the heat dissipation fins 211 on the top of the housing 210 before being discharged from the ventilation opening 150 on the other side, thereby removing heat from the top heat dissipation fins 211.

[0051] In this approach, considering that the airflow and velocity at the bottom heat dissipation fins 211 of the housing 210 are greater than those at the top heat dissipation fins 211, the components in the circuit module 220 that generate more heat can be attached and fixed to the inner wall at the bottom of the housing 210, while the components that generate less heat can be attached and fixed to the inner wall at the top of the housing 210, so as to meet the heat dissipation requirements of different components.

[0052] To optimize the airflow at the top heat dissipation fins 211 of the housing 210, this application further proposes an implementation method, which can be found in the following description. Figure 7 The ventilation opening 150 includes an air inlet 151 and an air outlet 152. The air inlet 151 is located on the front side of the housing 210 along the direction indicated by the double arrow Y, that is, the air inlet 151 is located on the side of the housing 210 facing the direction of the carrier's movement (pointed to by arrow Y1 in the figure). The air outlet 152 is located on the rear side of the housing 210 along the direction indicated by the double arrow Y, that is, the air outlet 152 is located on the side of the housing 210 facing the opposite direction of the carrier's movement (pointed to by arrow Y2 in the figure).

[0053] exist Figure 7 In the specific embodiment shown, the housing 210 is spaced apart from the front edge of the opening 121 to form the air inlet 151. The air outlet 152 is formed on the adapter 120 and spaced apart from the opening 121. In some other embodiments, the air inlet 151 and the air outlet 152 may both be formed by the housing 210 being spaced apart from the edge of the opening 121, or they may both be formed independently at a position spaced apart from the opening 121.

[0054] The area of ​​the air inlet 151 is larger than that of the air outlet 152. The larger air inlet 151 can absorb more air, creating a stronger internal negative pressure in the second air duct 142. The smaller air outlet 152 can increase the airflow speed, creating a high-pressure area at the air outlet 152, allowing the gas to be discharged more quickly and in a concentrated manner, thus achieving efficient heat dissipation of the heat sink 211 on the top of the casing 210.

[0055] Further, please refer to Figure 8 Based on the spaced front edges of the housing 210 and the opening 121 to form a large-area air inlet 151, the housing 210 can be provided with an interface 213 on the front side in the direction indicated by the double arrow Y. The interface 213 is used to connect to external devices (such as drone countermeasure devices, computers, etc.) through a wire harness. The air inlet 151 not only allows air to enter, but also allows the wire harness to pass through for routing. The large-area air inlet 151 formed by the front side of the opening 121 can maximize the convenience of connecting the wire harness plug to the interface 213.

[0056] Please combine Figure 7 and Figure 8 Interfaces 213 can be provided on both the front and rear sides of the housing 210, and the air inlet 151 on the front side and the air outlet 152 on the rear side can be used for wiring. In the case that the area of ​​the air inlet 151 on the front side is larger than that of the air outlet 152 on the rear side, more interfaces 213 can be provided on the front side to meet the space required for each wiring.

[0057] When moving with a carrier, taking a vehicle as an example, the vehicle moves in the direction indicated by the double arrow Y in the figure. During the movement, the vehicle will start, stop, and turn, with the frequency of starting and stopping being higher than that of turning. When encountering potholes, the vehicle will also experience bumps.

[0058] For damping and shock absorption, when the vehicle body starts and stops, the equipment body 200 will vibrate in the front-to-back direction (in the direction indicated by the double arrow Y) relative to the support frame 110. When turning, the equipment body 200 will vibrate in the left-to-right direction (in the direction indicated by the double arrow X) relative to the support frame 110. When bumps occur, the equipment body 200 will vibrate in the up-down direction (in the direction indicated by the double arrow Z) relative to the support frame 110.

[0059] Considering that if the device body 200 vibrates significantly relative to the vehicle body, it will affect the transmission and reception of radiated signals, thus causing deviations in the detection and positioning of the UAV.

[0060] Based on this, considering the motion characteristics of the UAV detection device 10 as it moves with the carrier, and in order to suppress large-amplitude vibrations of the device body 200 as much as possible while providing a certain degree of vibration damping and buffering, this application proposes an implementation method for the structural design of the vibration damping component 130. Please refer to [link / reference] for details. Figure 9The figure shows the exploded structure of the mounting base 100. As shown, the damping component 130 includes a first connecting block 131, a second connecting block 132, and a damping spring 133. The first connecting block 131 is fixed to the top of the support frame 110, and the second connecting block 132 is fixed to the bottom of the adapter frame 120. The first connecting block 131 and the second connecting block 132 are arranged opposite each other in the vertical direction (indicated by the double arrow Z in the figure, which is perpendicular to the directions indicated by the double arrows X and Y). The damping spring 133 extends spirally and passes through and is fixed to the first connecting block 131 and the second connecting block 132 respectively. The axial direction of each damping spring 133 is parallel to the direction indicated by the double arrow Y.

[0061] Since the damping spring 133 extends spirally along the direction indicated by the double arrow Y, and is respectively fixed to the first connecting block 131 and the second connecting block 132, the first connecting block 131 and the second connecting block 132 can suppress the deformation of the damping spring 133 along the direction indicated by the double arrow Y to a large extent. As a result, the frequent start and stop of the vehicle body will not cause the equipment body 200 to produce a large amplitude of front and rear vibration, thus suppressing the vibration amplitude of the equipment body 200 in the front and rear direction.

[0062] For the damping element 130 arranged in this way, the left and right directions (direction indicated by double arrow X) and the up and down directions (direction indicated by double arrow Z) are both radial directions of the damping spring 133. Since the damping spring 133 has relatively weak deformation capability in the radial direction, it can also effectively suppress the vibration amplitude of the equipment body 200 in the left and right and up and down directions while playing a certain role in buffering and damping vibration.

[0063] To further enhance the suppression of vibration amplitude of the equipment body 200 by the damping spring 133 in the front-to-back direction, further improvements were made to the damping component 130, such as... Figure 10 The side structure of the damping element 130 shown in the figure shows that the damping spring 133 can be divided into a first part 1331 and a second part 1332 along the axial direction (in the direction indicated by the double arrow Y). The first part 1331 and the second part 1332 are radially symmetrical with respect to the plane M perpendicular to the direction indicated by the double arrow Y.

[0064] from Figure 10 As can be seen from this, in this embodiment, after the first part 1331 and the second part 1332 are mirror-symmetrically arranged, their spiral directions are different. This causes the device body 200 fixed to the second connecting block 132 to move forward relative to the support frame 110 fixed to the first connecting block 131. Figure 10 When the trend is to move to the left from the perspective of the second part 1332 spiral, the tilt direction produced by the spiral is ( Figure 10The tilt (from lower left to upper right) from a viewing angle strongly suppresses this tendency to move, thus preventing the device body 200 from generating large amplitudes. Conversely, the second connecting block 132 moves backward relative to the first connecting block 131 ( Figure 10 When the trend is to move to the right (from the perspective), the first part 1331 will generate strong suppression.

[0065] To ensure the stability of the UAV detection equipment 10 mounted on the carrier and to better suppress the vibration amplitude of the equipment body 200, such as Figure 9 As shown, multiple vibration damping elements 130 can be provided on each side of the support frame 110 and the adapter frame 120 along the direction indicated by the double arrow X. The figure shows two on each side as an example. Of course, in some other embodiments, three or more can be provided on each side. The specific number is not limited here.

[0066] Please see Figure 11 The figure shows a top view of the housing 210 in its open state. In some embodiments, the housing 210 may include an upper housing 214 and a lower housing 215, which are interlocked and rotatably connected on one side. By rotating the upper housing 214, the housing 210 can be quickly opened and closed, thereby facilitating the disassembly and maintenance of the internal circuit module 220.

[0067] Please continue reading. Figure 11 In some embodiments, circuit module 220 may include a spectrum detection module 221, a detection control processing module 222, an overall control scheduling module 223, a power conversion module 224, a communication routing module 225, a power divider module 226, and a communication antenna 227. Specifically, the power divider module 226 amplifies the signal collected by antenna 240 and distributes it to the spectrum detection module 221 and the detection control processing module 222; the spectrum detection module 221 processes and analyzes the full-band radio signals after power division amplification; the detection control processing module 222 processes and analyzes the relevant Drone ID and Roome ID UAV information after power division amplification; the overall control scheduling module 223 realizes data fusion and distribution between different modules; the power conversion module 224 meets the power supply requirements of different operating conditions and different modules; and the communication routing module 225 uses the communication antenna 227 to realize cloud communication reporting of the analyzed UAV information and output reconnaissance and strike linkage signals.

[0068] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and not to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application. In particular, as long as there is no structural conflict, the various technical features mentioned in the various embodiments can be combined in any way.

Claims

1. An unmanned aerial vehicle detection apparatus, comprising: The unmanned aerial vehicle detection device comprises: a mounting seat comprising: a support frame for fixedly mounting on a carrier; an adapter frame arranged above the support frame, the adapter frame being provided with an opening, and a first air duct being formed between the bottom of the adapter frame and the top of the support frame; a plurality of damping members connected between the top of the support frame and the bottom of the adapter frame, the damping members being arranged on both sides of the support frame and the adapter frame along a first direction, wherein the first direction is perpendicular to the moving direction of the carrier; a device body comprising: a shell fixedly connected to the adapter frame on both sides along the first direction, the top and bottom of the shell being provided with a plurality of heat dissipation fins extending along a second direction, the heat dissipation fins being arranged at intervals along the first direction, and the heat dissipation fins on the bottom of the shell extending at least partially into the first air duct from the opening, wherein the second direction is perpendicular to the first direction, a circuit module fixedly attached to the inner wall of the shell.

2. The drone detection device of claim 1, wherein, The shell is provided with a support arm on both sides along the first direction, and the support arm is lapped and fixed to the adapter frame.

3. The drone detection device of claim 1, wherein, The device body further comprises a shielding cover and an antenna, the shielding cover covering the heat dissipation fins on the top of the shell, the antenna being arranged on the shielding cover, and the antenna being electrically connected to the circuit module; the shielding cover is provided with a ventilation opening on both sides along the second direction, and the ventilation opening is arranged opposite to the heat dissipation fins on the top of the shell.

4. The drone detection apparatus of claim 3, wherein, The unmanned aerial vehicle detection device further comprises a protective cover, the protective cover covering the top and the periphery of the device body, the shielding cover and the antenna; the adapter frame is provided with a ventilation opening at a position on both sides of the shell along the second direction, the edge of the bottom of the protective cover is connected to the adapter frame, and a second air duct is formed between both sides of the shell along the second direction and the protective cover.

5. The drone detection apparatus of claim 4, wherein, The ventilation opening comprises an air inlet and an air outlet, the air inlet is located on the front side of the shell along the second direction, the air outlet is located on the rear side of the shell along the second direction, and the area of the air inlet is greater than that of the air outlet.

6. The drone detection device of claim 5, wherein, The shell is spaced apart from the front edge of the opening along the second direction to form the air inlet; the shell is provided with an interface on the front side along the second direction, the interface is used for connecting with an external device through a wire harness, and the air inlet is used for allowing the wire harness to pass through.

7. The drone detection apparatus of any one of claims 1-6, wherein, The damping member comprises a first connecting block, a second connecting block and a damping spring; the first connecting block is fixed to the top of the support frame, the second connecting block is fixed to the bottom of the adapter frame, and the first connecting block and the second connecting block are arranged opposite to each other along a vertical direction, wherein the vertical direction is perpendicular to both the first direction and the second direction; the damping spring is helically extended and fixed to the first connecting block and the second connecting block, respectively; the axial direction of each damping spring is parallel to the second direction.

8. The drone detection apparatus of claim 7, wherein, The damping spring is divided into a first part and a second part along the axial direction, and the first part and the second part are mirror-symmetric relative to a plane perpendicular to the second direction.

9. The drone detection device of claim 7, wherein, A plurality of damping members are arranged between the support frame and the adapter frame on each side in the first direction.

10. The drone detection device of any one of claims 1-6, wherein, The shell comprises an upper shell and a lower shell, the upper shell and the lower shell are buckled to each other and are connected on one side.

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